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RU2012145092A - GAS-TURBINE ENGINE OPERATING ON A POOLED FUEL MIXTURE - Google Patents

GAS-TURBINE ENGINE OPERATING ON A POOLED FUEL MIXTURE Download PDF

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Publication number
RU2012145092A
RU2012145092A RU2012145092/06A RU2012145092A RU2012145092A RU 2012145092 A RU2012145092 A RU 2012145092A RU 2012145092/06 A RU2012145092/06 A RU 2012145092/06A RU 2012145092 A RU2012145092 A RU 2012145092A RU 2012145092 A RU2012145092 A RU 2012145092A
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RU
Russia
Prior art keywords
gas
turbine engine
supplied
heating
gas turbine
Prior art date
Application number
RU2012145092/06A
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Russian (ru)
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RU2521179C2 (en
Inventor
Йосихиро ЯМАСАКИ
Со КУРОСАКА
Хироюки КАСИХАРА
Original Assignee
Кавасаки Дзюкогио Кабусики Кайся
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Publication of RU2012145092A publication Critical patent/RU2012145092A/en
Application granted granted Critical
Publication of RU2521179C2 publication Critical patent/RU2521179C2/en

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01N—GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR MACHINES OR ENGINES IN GENERAL; GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR INTERNAL-COMBUSTION ENGINES
    • F01N3/00—Exhaust or silencing apparatus having means for purifying, rendering innocuous, or otherwise treating exhaust
    • F01N3/08—Exhaust or silencing apparatus having means for purifying, rendering innocuous, or otherwise treating exhaust for rendering innocuous
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/08—Heating air supply before combustion, e.g. by exhaust gases
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/40—Continuous combustion chambers using liquid or gaseous fuel characterised by the use of catalytic means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00002—Gas turbine combustors adapted for fuels having low heating value [LHV]

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Exhaust Gas After Treatment (AREA)
  • Supercharger (AREA)

Abstract

1. Газотурбинный двигатель, работающий на обедненной топливной смеси, содержащий:компрессор, предназначенный для сжатия рабочего газа для создания сжатого газа, при этом рабочий газ имеет концентрацию горючего компонента, которая меньше его предела воспламеняемости;каталитическую камеру сгорания, предназначенную для сжигания сжатого газа посредством каталитической реакции с помощью катализатора, размещенного в ней, для образования газообразных продуктов сгорания;турбину, выполненную с возможностью приведения ее в действие посредством газообразных продуктов сгорания, подаваемых из каталитической камеры сгорания;регенеративный теплообменник, предназначенный для нагрева сжатого газа, подаваемого из компрессора в каталитическую камеру сгорания, посредством отработавшего газа, подаваемого из турбины по каналу для отработавшего газа в регенеративный теплообменник;горелку, предназначенную для сжигания газа, отбираемого из компрессора, вместе с топливом для образования нагревающего газа и подачи нагревающего газа в канал для отработавшего газа; иклапан, предназначенный для регулирования количества отбираемого газа, подлежащего подаче в горелку.2. Газотурбинный двигатель по п.1, в котором клапан выполнен с возможностью непрерывного увеличения или уменьшения количества отбираемого газа, подлежащего подаче в нагревательную горелку.3. Газотурбинный двигатель по п.1 или 2, в котором нагревательная горелка приводится в действие при операции запуска газотурбинного двигателя.4. Газотурбинный двигатель по п.3, в котором нагревательная горелка работает в состоянии, когда газотурбинный двигатель работает в н�1. A gas turbine engine operating on a lean fuel mixture, comprising: a compressor designed to compress a working gas to create a compressed gas, while the working gas has a concentration of a combustible component that is less than its flammability limit; a catalytic combustion chamber designed to burn compressed gas by catalytic reaction with the help of a catalyst placed therein to form gaseous combustion products; a turbine configured to be driven by means of combustion gases supplied from the catalytic combustion chamber; a regenerative heat exchanger designed to heat the compressed gas supplied from the compressor to the catalytic a combustion chamber, by means of exhaust gas supplied from the turbine through an exhaust gas duct to a regenerative heat exchanger; a burner designed to burn gas taken from the compressor together with fuel to form heating gas and hearth chi heating gas into the exhaust gas duct; and a valve for regulating the amount of bleed gas to be supplied to the burner. 2. The gas turbine engine of claim 1, wherein the valve is configured to continuously increase or decrease the amount of bleed gas to be supplied to the heating burner. A gas turbine engine according to claim 1 or 2, wherein the heating burner is driven during the operation of starting the gas turbine engine. The gas turbine engine of claim 3, wherein the heating burner is operated in a state where the gas turbine engine is operated

Claims (5)

1. Газотурбинный двигатель, работающий на обедненной топливной смеси, содержащий:1. A gas turbine engine running on a lean fuel mixture, comprising: компрессор, предназначенный для сжатия рабочего газа для создания сжатого газа, при этом рабочий газ имеет концентрацию горючего компонента, которая меньше его предела воспламеняемости;a compressor designed to compress the working gas to create compressed gas, while the working gas has a concentration of a combustible component that is less than its flammability limit; каталитическую камеру сгорания, предназначенную для сжигания сжатого газа посредством каталитической реакции с помощью катализатора, размещенного в ней, для образования газообразных продуктов сгорания;a catalytic combustion chamber for burning compressed gas by means of a catalytic reaction using a catalyst placed therein to form gaseous products of combustion; турбину, выполненную с возможностью приведения ее в действие посредством газообразных продуктов сгорания, подаваемых из каталитической камеры сгорания;a turbine configured to drive it by means of gaseous products of combustion supplied from the catalytic combustion chamber; регенеративный теплообменник, предназначенный для нагрева сжатого газа, подаваемого из компрессора в каталитическую камеру сгорания, посредством отработавшего газа, подаваемого из турбины по каналу для отработавшего газа в регенеративный теплообменник;a regenerative heat exchanger for heating the compressed gas supplied from the compressor to the catalytic combustion chamber by means of exhaust gas supplied from the turbine through the exhaust gas channel to the regenerative heat exchanger; горелку, предназначенную для сжигания газа, отбираемого из компрессора, вместе с топливом для образования нагревающего газа и подачи нагревающего газа в канал для отработавшего газа; иa burner designed to burn gas taken from the compressor, together with fuel, to form heating gas and supply heating gas to the exhaust gas channel; and клапан, предназначенный для регулирования количества отбираемого газа, подлежащего подаче в горелку.a valve designed to control the amount of sampled gas to be supplied to the burner. 2. Газотурбинный двигатель по п.1, в котором клапан выполнен с возможностью непрерывного увеличения или уменьшения количества отбираемого газа, подлежащего подаче в нагревательную горелку.2. The gas turbine engine according to claim 1, wherein the valve is configured to continuously increase or decrease the amount of sampled gas to be supplied to the heating burner. 3. Газотурбинный двигатель по п.1 или 2, в котором нагревательная горелка приводится в действие при операции запуска газотурбинного двигателя.3. The gas turbine engine according to claim 1 or 2, in which the heating burner is activated during the operation of starting the gas turbine engine. 4. Газотурбинный двигатель по п.3, в котором нагревательная горелка работает в состоянии, когда газотурбинный двигатель работает в неноминальном режиме работы, при котором число оборотов меньше числа оборотов при номинальном режиме работы газотурбинного двигателя.4. The gas turbine engine according to claim 3, in which the heating burner is operating in a state where the gas turbine engine is operating in a non-nominal mode of operation, in which the number of revolutions is less than the number of revolutions in the nominal mode of operation of the gas turbine engine. 5. Газотурбинный двигатель по п.1 или 2, в котором нагревательная горелка работает, когда имеет место нарушение нормального процесса горения в каталитической камере сгорания. 5. The gas turbine engine according to claim 1 or 2, in which the heating burner operates when there is a violation of the normal combustion process in the catalytic combustion chamber.
RU2012145092/06A 2010-03-24 2011-03-07 Gas turbine engine running on lean fuel mix RU2521179C2 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
JP2010067271A JP4751950B1 (en) 2010-03-24 2010-03-24 Lean fuel intake gas turbine
JP2010-067271 2010-03-24
PCT/JP2011/055210 WO2011118372A1 (en) 2010-03-24 2011-03-07 Lean-fuel intake gas turbine

Publications (2)

Publication Number Publication Date
RU2012145092A true RU2012145092A (en) 2014-04-27
RU2521179C2 RU2521179C2 (en) 2014-06-27

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RU2012145092/06A RU2521179C2 (en) 2010-03-24 2011-03-07 Gas turbine engine running on lean fuel mix

Country Status (7)

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US (1) US20130276433A1 (en)
JP (1) JP4751950B1 (en)
CN (1) CN102933819A (en)
AU (1) AU2011230790B2 (en)
RU (1) RU2521179C2 (en)
UA (1) UA102361C2 (en)
WO (1) WO2011118372A1 (en)

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Publication number Publication date
AU2011230790B2 (en) 2014-09-18
JP2011196355A (en) 2011-10-06
JP4751950B1 (en) 2011-08-17
WO2011118372A1 (en) 2011-09-29
RU2521179C2 (en) 2014-06-27
CN102933819A (en) 2013-02-13
US20130276433A1 (en) 2013-10-24
UA102361C2 (en) 2013-06-25
AU2011230790A1 (en) 2012-11-08

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